EP3238859B1 - Method and assembly for forming components using a jacketed core - Google Patents

Method and assembly for forming components using a jacketed core Download PDF

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Publication number
EP3238859B1
EP3238859B1 EP17168418.6A EP17168418A EP3238859B1 EP 3238859 B1 EP3238859 B1 EP 3238859B1 EP 17168418 A EP17168418 A EP 17168418A EP 3238859 B1 EP3238859 B1 EP 3238859B1
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EP
European Patent Office
Prior art keywords
wall
jacket
component
core
jacketed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17168418.6A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3238859A1 (en
Inventor
James Albert Tallman
Stephen Francis Rutkowski
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General Electric Co
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General Electric Co
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Filing date
Publication date
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Publication of EP3238859A1 publication Critical patent/EP3238859A1/en
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Publication of EP3238859B1 publication Critical patent/EP3238859B1/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/0054—Casting in, on, or around objects which form part of the product rotors, stators for electrical motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/02—Lost patterns
    • B22C7/023—Patterns made from expanded plastic materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/06—Permanent moulds for shaped castings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/22—Moulds for peculiarly-shaped castings
    • B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/005—Adjustable, sectional, expandable or flexible patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B22C9/046—Use of patterns which are eliminated by the liquid metal in the mould
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/101—Permanent cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/103—Multipart cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/106—Vented or reinforced cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/108—Installation of cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/12—Treating moulds or cores, e.g. drying, hardening
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/0072—Casting in, on, or around objects which form part of the product for making objects with integrated channels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/0081—Casting in, on, or around objects which form part of the product pretreatment of the insert, e.g. for enhancing the bonding between insert and surrounding cast metal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/182—Transpiration cooling
    • F01D5/183—Blade walls being porous
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the field of the disclosure relates generally to components having an outer wall of a preselected thickness, and more particularly to forming such components using a jacketed core.
  • Some components require an outer wall to be formed with a preselected thickness, for example, in order to perform an intended function.
  • some components such as hot gas path components of gas turbines, are subjected to high temperatures.
  • At least some such components have internal voids defined therein, such as but not limited to a network of plenums and passages, to receive a flow of a cooling fluid adjacent the outer wall, and an efficacy of the cooling provided is related to the thickness of the outer wall.
  • At least some known components having a preselected outer wall thickness are formed in a mold, with a core of ceramic material positioned within the mold cavity.
  • a molten metal alloy is introduced around the ceramic core and cooled to form the component, and the outer wall of the component is defined between the ceramic core and an interior wall of the mold cavity.
  • an ability to produce a consistent preselected outer wall thickness of the cast component depends on an ability to precisely position the core relative to the mold to define the cavity space between the core and the mold.
  • the core is positioned with respect to the mold cavity by a plurality of platinum locating pins.
  • Such precise and consistent positioning is complex and labor-intensive in at least some cases, and leads to a reduced yield rate for successfully cast components, in particular for, but not limited to, cases in which a preselected outer wall thickness of the component is relatively thin.
  • the core and mold shift, shrink, and/or twist with respect to each other during the final firing before the casting pour, thereby altering the initial cavity space dimensions between the core and the mold and, consequently, the thickness of the outer wall of the cast component.
  • at least some known ceramic cores are fragile, resulting in cores that are difficult and expensive to produce and handle without damage during the complex and labor-intensive process.
  • At least some known components having a preselected outer wall thickness are formed by drilling and/or otherwise machining the component to obtain the outer wall thickness, such as, but not limited to, using an electrochemical machining process.
  • at least some such machining processes are relatively time-consuming and expensive.
  • at least some such machining processes cannot produce an outer wall having the preselected thickness, shape, and/or curvature required for certain component designs.
  • US 2010/304064 describes a method for producing a cast part from metal, a metal alloy or from plastic, with at least one complex internal structure.
  • EP 0190114 describes a molded metal object comprising one or more channels or cavities, along with a method of manufacturing the molded metal object.
  • US 5291654 describes a method for casting metering holes connecting the inner and outer surfaces of hollow investment cast objects, such as hollow air cooled gas turbine airfoils.
  • US 5950705 describes a method for casting and controlling wall thickness.
  • a mold assembly for use in forming a component from a component material.
  • the component has an outer wall of a predetermined thickness.
  • the mold assembly includes a mold that includes an interior wall that defines a mold cavity within the mold.
  • the mold assembly also includes a jacketed core positioned with respect to the mold.
  • the jacketed core includes a jacket.
  • the jacket includes a first jacket outer wall coupled against the interior wall, a second jacket outer wall positioned interiorly from the first jacket outer wall, and at least one jacketed cavity defined therebetween.
  • the at least one jacketed cavity is configured to receive the component material in a molten state therein.
  • the jacketed core also includes a core positioned interiorly from the second jacket outer wall.
  • the core includes a perimeter coupled against the second jacket outer wall. The jacket separates the perimeter from the interior wall by the predetermined thickness, such that the outer wall is formable therebetween the perimeter and the interior wall.
  • a method of forming a component having an outer wall of a predetermined thickness includes introducing a component material in a molten state into at least one jacketed cavity defined in a mold assembly.
  • the mold assembly includes a jacketed core positioned with respect to a mold.
  • the mold includes an interior wall that defines a mold cavity within the mold.
  • the jacketed core includes a jacket that includes a first jacket outer wall coupled against the interior wall, a second jacket outer wall positioned interiorly from the first jacket outer wall, and the at least one jacketed cavity defined therebetween.
  • the jacketed core also includes a core positioned interiorly from the second jacket outer wall.
  • the core includes a perimeter coupled against the second jacket outer wall.
  • the jacket separates the perimeter from the interior wall by the predetermined thickness.
  • the method also includes cooling the component material to form the component. The perimeter and the interior wall cooperate to define the outer wall of the component therebetween.
  • Approximating language may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms such as "about,” “approximately,” and “substantially” is not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value.
  • range limitations may be identified. Such ranges may be combined and/or interchanged, and include all the sub-ranges contained therein unless context or language indicates otherwise.
  • the exemplary components and methods described herein overcome at least some of the disadvantages associated with known assemblies and methods for forming a component having an outer wall of a predetermined thickness.
  • the embodiments described herein include forming a precursor component shaped to correspond to a shape of at least portions of the component, and forming a jacket around the precursor component.
  • a core is added to the jacketed precursor component, and the precursor component material is removed to form a jacketed core.
  • the jacketed core includes a jacket formed without the precursor component, and/or a core formed in a separate core-forming process.
  • the jacketed core is positioned with respect to a mold, and the component is cast in at least one jacketed cavity defined between jacket outer walls, such that the jacket separates a perimeter of the core from an interior wall of the mold by the predetermined thickness.
  • the core perimeter and mold interior wall cooperate to define the outer wall of the component therebetween.
  • FIG. 1 is a schematic view of an exemplary rotary machine 10 having components for which embodiments of the current disclosure may be used.
  • rotary machine 10 is a gas turbine that includes an intake section 12, a compressor section 14 coupled downstream from intake section 12, a combustor section 16 coupled downstream from compressor section 14, a turbine section 18 coupled downstream from combustor section 16, and an exhaust section 20 coupled downstream from turbine section 18.
  • a generally tubular casing 36 at least partially encloses one or more of intake section 12, compressor section 14, combustor section 16, turbine section 18, and exhaust section 20.
  • rotary machine 10 is any rotary machine for which components formed with internal passages as described herein are suitable.
  • embodiments of the present disclosure are described in the context of a rotary machine for purposes of illustration, it should be understood that the embodiments described herein are applicable in any context that involves a component suitably formed with a preselected outer wall thickness.
  • turbine section 18 is coupled to compressor section 14 via a rotor shaft 22.
  • the term “couple” is not limited to a direct mechanical, electrical, and/or communication connection between components, but may also include an indirect mechanical, electrical, and/or communication connection between multiple components.
  • compressor section 14 compresses the air to a higher pressure and temperature. More specifically, rotor shaft 22 imparts rotational energy to at least one circumferential row of compressor blades 40 coupled to rotor shaft 22 within compressor section 14. In the exemplary embodiment, each row of compressor blades 40 is preceded by a circumferential row of compressor stator vanes 42 extending radially inward from casing 36 that direct the air flow into compressor blades 40. The rotational energy of compressor blades 40 increases a pressure and temperature of the air. Compressor section 14 discharges the compressed air towards combustor section 16.
  • combustor section 16 the compressed air is mixed with fuel and ignited to generate combustion gases that are channeled towards turbine section 18. More specifically, combustor section 16 includes at least one combustor 24, in which a fuel, for example, natural gas and/or fuel oil, is injected into the air flow, and the fuel-air mixture is ignited to generate high temperature combustion gases that are channeled towards turbine section 18.
  • a fuel for example, natural gas and/or fuel oil
  • Turbine section 18 converts the thermal energy from the combustion gas stream to mechanical rotational energy. More specifically, the combustion gases impart rotational energy to at least one circumferential row of rotor blades 70 coupled to rotor shaft 22 within turbine section 18. In the exemplary embodiment, each row of rotor blades 70 is preceded by a circumferential row of turbine stator vanes 72 extending radially inward from casing 36 that direct the combustion gases into rotor blades 70.
  • Rotor shaft 22 may be coupled to a load (not shown) such as, but not limited to, an electrical generator and/or a mechanical drive application.
  • the exhausted combustion gases flow downstream from turbine section 18 into exhaust section 20.
  • Components of rotary machine 10 are designated as components 80.
  • Components 80 proximate a path of the combustion gases are subjected to high temperatures during operation of rotary machine 10. Additionally or alternatively, components 80 include any component suitably formed with a preselected outer wall thickness.
  • FIG. 2 is a schematic perspective view of an exemplary component 80, illustrated for use with rotary machine 10 (shown in FIG. 1 ).
  • FIG. 3 is a schematic cross-section of component 80, taken along lines 3-3 shown in FIG. 2 .
  • FIG. 4 is a schematic perspective sectional view of a portion of component 80, designated as portion 4 in FIG. 3 .
  • component 80 includes an outer wall 94 having a preselected thickness 104.
  • component 80 includes at least one internal void 100 defined therein.
  • a cooling fluid is provided to internal void 100 during operation of rotary machine 10 to facilitate maintaining component 80 below a temperature of the hot combustion gases.
  • Component 80 is formed from a component material 78.
  • component material 78 is a suitable nickel-based superalloy.
  • component material 78 is at least one of a cobalt-based superalloy, an iron-based alloy, and a titanium-based alloy.
  • component material 78 is any suitable material that enables component 80 to be formed as described herein.
  • component 80 is one of rotor blades 70 or stator vanes 72.
  • component 80 is another suitable component of rotary machine 10 that is capable of being formed with a preselected outer wall thickness as described herein.
  • component 80 is any component for any suitable application that is suitably formed with a preselected outer wall thickness.
  • rotor blade 70 in the exemplary embodiment, includes a pressure side 74 and an opposite suction side 76. Each of pressure side 74 and suction side 76 extends from a leading edge 84 to an opposite trailing edge 86.
  • rotor blade 70, or alternatively stator vane 72 extends from a root end 88 to an opposite tip end 90. A longitudinal axis 89 of component 80 is defined between root end 88 and tip end 90.
  • rotor blade 70, or alternatively stator vane 72 has any suitable configuration that is capable of being formed with a preselected outer wall thickness as described herein.
  • Outer wall 94 at least partially defines an exterior surface 92 of component 80.
  • outer wall 94 extends circumferentially between leading edge 84 and trailing edge 86, and also extends longitudinally between root end 88 and tip end 90.
  • outer wall 94 extends to any suitable extent that enables component 80 to function for its intended purpose.
  • Outer wall 94 is formed from component material 78.
  • component 80 includes an inner wall 96 having a preselected thickness 107.
  • Inner wall 96 is positioned interiorly to outer wall 94, and the at least one internal void 100 includes at least one plenum 110 that is at least partially defined by inner wall 96 and interior thereto.
  • each plenum 110 extends from root end 88 to proximate tip end 90.
  • each plenum 110 extends within component 80 in any suitable fashion, and to any suitable extent, that enables component 80 to be formed as described herein.
  • the at least one plenum 110 includes a plurality of plenums 110, each defined by inner wall 96 and at least one partition wall 95 that extends between pressure side 74 and suction side 76.
  • the at least one internal void 100 includes any suitable number of plenums 110 defined in any suitable fashion.
  • Inner wall 96 is formed from component material 78.
  • At least a portion of inner wall 96 extends circumferentially and longitudinally adjacent at least a portion of outer wall 94 and is separated therefrom by an offset distance 98, such that the at least one internal void 100 also includes at least one chamber 112 defined between inner wall 96 and outer wall 94.
  • the at least one chamber 112 includes a plurality of chambers 112 each defined by outer wall 94, inner wall 96, and at least one partition wall 95.
  • the at least one chamber 112 includes any suitable number of chambers 112 defined in any suitable fashion.
  • inner wall 96 includes a plurality of apertures 102 defined therein and extending therethrough, such that each chamber 112 is in flow communication with at least one plenum 110.
  • offset distance 98 is selected to facilitate effective impingement cooling of outer wall 94 by cooling fluid supplied through plenums 110 and emitted through apertures 102 defined in inner wall 96.
  • offset distance 98 varies circumferentially and/or longitudinally along component 80 to facilitate local cooling requirements along respective portions of outer wall 94.
  • component 80 is not configured for impingement cooling, and offset distance 98 is selected in any suitable fashion.
  • the at least one internal void 100 further includes at least one return channel 114 at least partially defined by inner wall 96.
  • Each return channel 114 is in flow communication with at least one chamber 112, such that each return channel 114 provides a return fluid flow path for fluid used for impingement cooling of outer wall 94.
  • each return channel 114 extends from root end 88 to proximate tip end 90.
  • each return channel 114 extends within component 80 in any suitable fashion, and to any suitable extent, that enables component 80 to be formed as described herein.
  • the at least one return channel 114 includes a plurality of return channels 114, each defined by inner wall 96 adjacent one of chambers 112.
  • the at least one return channel 114 includes any suitable number of return channels 114 defined in any suitable fashion.
  • cooling fluid is supplied to plenums 110 through root end 88 of component 80. As the cooling fluid flows generally towards tip end 90, portions of the cooling fluid are forced through apertures 102 into chambers 112 and impinge upon outer wall 94. The used cooling fluid then flows into return channels 114 and flows generally toward root end 88 and out of component 80.
  • the arrangement of the at least one plenum 110, the at least one chamber 112, and the at least one return channel 114 forms a portion of a cooling circuit of rotary machine 10, such that used cooling fluid is returned to a working fluid flow through rotary machine 10 upstream of combustor section 16 (shown in FIG. 1 ).
  • impingement flow through plenums 110 and chambers 112 and return flow through channels 114 is described in terms of embodiments in which component 80 is rotor blade 70 and/or stator vane 72, it should be understood that this disclosure contemplates a circuit of plenums 110, chambers 112, and return channels 114 for any suitable component 80 of rotary machine 10, and additionally for any suitable component 80 for any other application suitable for closed circuit fluid flow through a component.
  • Such embodiments provide an improved operating efficiency for rotary machine 10 as compared to cooling systems that exhaust used cooling fluid directly from component 80 into the working fluid within turbine section 18.
  • the at least one internal void 100 does not include return channels 114.
  • outer wall 96 includes openings extending therethrough (not shown), and the cooling fluid is exhausted into the working fluid through the outer wall openings to facilitate film cooling of exterior surface 92.
  • component 80 includes both return channels 114 and openings (not shown) extending through outer wall 94, a first portion of the cooling fluid is returned to a working fluid flow through rotary machine 10 upstream of combustor section 16 (shown in FIG. 1 ), and a second portion of the cooling fluid is exhausted into the working fluid through the outer wall openings to facilitate film cooling of exterior surface 92.
  • component 80 is any suitable component for any suitable application, and includes any suitable number, type, and arrangement of internal voids 100 that enable component 80 to function for its intended purpose.
  • outer wall 94 has a thickness 104 preselected to facilitate impingement cooling of outer wall 94 with a reduced amount of cooling fluid flow as compared to components having thicker outer walls.
  • outer wall thickness 104 is any suitable thickness that enables component 80 to function for its intended purpose.
  • outer wall thickness 104 varies along outer wall 94.
  • outer wall thickness 104 is constant along outer wall 94.
  • apertures 102 each have a substantially circular cross-section. In alternative embodiments, apertures 102 each have a substantially ovoid cross-section. In other alternative embodiments, apertures 102 each have any suitable shape that enables apertures 102 to be function as described herein.
  • FIG. 5 is a schematic perspective view of an exemplary precursor component 580 that may be used to form component 80 shown in FIGs. 2-4 .
  • FIG. 6 is a schematic perspective sectional view of a portion of precursor component 580, taken along lines 6-6 in FIG. 5 , and corresponding to the portion of component 80 shown in FIG. 4 .
  • precursor component 580 is formed from a precursor material 578 and has a shape corresponding to a shape of at least portions of component 80. More specifically, in certain embodiments, precursor component 580 has a shape corresponding to the shape of component 80, except an outer wall 594 of precursor component 580 includes at least one outer wall aperture 520 defined therein and extending therethrough.
  • outer wall 594 otherwise corresponds to the shape of outer wall 94 of component 80, the at least one outer wall aperture 520 does not correspond to a feature of outer wall 94 of component 80.
  • outer wall 94 includes openings extending therethrough (not shown), for example to facilitate film cooling of exterior surface 92 of component 80 as described above, and precursor component outer wall apertures 520 are positioned and shaped to correspond to the openings defined through outer wall 94.
  • precursor component 580 does not include the at least one outer wall aperture 520.
  • a thickness 504 of outer wall 594 is reduced relative to thickness 104 of outer wall 94 by twice a thickness 706 of a jacket 700 to be applied to outer wall 594, as will be described herein.
  • thickness 504 is not reduced relative to thickness 104.
  • a thickness 507 of inner wall 596 is reduced relative to thickness 107 of inner wall 96 by twice thickness 706 of jacket 700 to be applied to inner wall 596, as will be described herein.
  • thickness 507 is not reduced relative to thickness 107.
  • precursor component 580 includes a pressure side 574 and an opposite suction side 576, a first end 588 and an opposite second end 590, and a leading edge 584 and an opposite trailing edge 586 shaped to correspond to pressure side 74, suction side 76, root end 88, tip end 90, leading edge 84, and trailing edge 86 of component 80.
  • precursor component 580 includes at least one internal void 500 that has a shape corresponding to the at least one void 100 of component 80.
  • precursor component 580 includes at least one plenum 510, at least one chamber 512, and at least one return channel 514 corresponding to the at least one plenum 110, the at least one chamber 112, and the at least one return channel 114 of component 80.
  • precursor component 580 includes an inner wall 596 corresponding to inner wall 96 of component 80, and inner wall apertures 502 defined in inner wall 596 corresponding to apertures 102 of component 80. In alternative embodiments, inner wall 596 does not include inner wall apertures 502.
  • precursor component 580 further includes at least one partition wall 595 that extends at least partially between pressure side 574 and suction side 576, corresponding to the at least one partition wall 95 of component 80.
  • each partition wall 595 extends from outer wall 594 of pressure side 574 to outer wall 594 of suction side 576.
  • at least one partition wall 595 extends from inner wall 596 of pressure side 574 to inner wall 596 of suction side 576.
  • at least one partition wall 595 extends from inner wall 596 to outer wall 594 of pressure side 574, and/or from inner wall 596 to outer wall 594 of suction side 576.
  • precursor component 580 includes outer wall 594 that at least partially defines an exterior surface 592 of precursor component 580.
  • Inner wall 596 extends circumferentially and longitudinally adjacent at least a portion of outer wall 594 and is separated therefrom by an offset distance 598, corresponding to offset distance 98 of component 80.
  • a shape of outer wall 594 and exterior surface 592 correspond to the shape of outer wall 94 and exterior surface 92 of component 80, except that, in the exemplary embodiment, outer wall 594 additionally includes the at least one outer wall aperture 520 defined therein and extending therethrough.
  • outer wall apertures 520 correspond in location and shape to the openings extending through outer wall 94.
  • the at least one outer wall aperture 520 facilitates forming at least one stand-off structure 720 (shown in FIG. 7 ) that facilitates maintaining an offset between a core 800 (shown in FIG. 8 ) and a mold 1000 (shown in FIG. 10 ) used to form component 80, as will be described herein.
  • precursor component 580 does not include outer wall apertures 520, and the at least one stand-off structure is formed by another suitable method, as will be described herein.
  • component 80 is any suitable component for any suitable application
  • precursor component 580 has a shape that corresponds to the shape of such component 80, except that in certain embodiments outer wall 594 includes at least one outer wall aperture 520 that does not correspond to a feature of outer wall 94 of component 80.
  • outer wall apertures 520 each extend from a first end 522, defined in exterior surface 592, to a second end 524, defined in a second surface 593 of outer wall 594 opposite exterior surface 592.
  • a diameter 526 of outer wall apertures 520 at second end 524 is selected to enable a jacket 700 (shown in FIG. 7 ) applied to outer wall 594 to form a closure 722 (shown in FIG. 7 ) at second end 524 of outer wall apertures 520, as will be described herein.
  • diameter 526 of outer wall apertures 520 at first end 522 is selected to enable jacket 700 applied to outer wall 594 to form closure 722 at first end 522 of outer wall apertures 520.
  • outer wall apertures 520 each define a generally frusto-conical shape through outer wall 594.
  • each outer wall aperture 520 defines any suitable shape that enables outer wall apertures 520 to function as described herein.
  • Closure 722 prevents an opening corresponding to aperture 520 from being formed in outer wall 94 when component 80 is formed.
  • outer wall apertures 520 are sized to correspond to the openings such that closure 722 is not formed, enabling later formation of the openings extending through outer wall 94.
  • precursor component 580 is formed at least partially using a suitable additive manufacturing process, and precursor material 578 is selected to facilitate additive manufacture of precursor component 580.
  • a computer design model of precursor component 580 is developed from a computer design model of component 80, with some embodiments including outer wall thickness 504 reduced and/or outer wall apertures 520 added, as described above, in the computer design model for precursor component 580.
  • the computer design model for precursor component 580 is sliced into a series of thin, parallel planes between first end 588 and second end 590 of precursor component 580.
  • a computer numerically controlled (CNC) machine deposits successive layers of precursor material 578 from first end 588 to second end 590 in accordance with the model slices to form precursor component 580. Three such representative layers are indicated as layers 566, 567, and 568.
  • precursor material 578 is selected to be a photopolymer, and the successive layers of precursor material 578 are deposited using a stereolithographic process.
  • precursor material 578 is selected to be a thermoplastic, and the successive layers of precursor material 578 are deposited using at least one of a fused filament fabrication process, an inkjet/powder bed process, a selective heat sintering process, and a selective laser sintering process.
  • precursor material 578 is selected to be any suitable material, and the successive layers of precursor material 578 are deposited using any suitable process that enables precursor component 580 to be formed as described herein. It should be understood that in certain embodiments, precursor component 580 is formed from a plurality of separately additively manufactured sections that are subsequently coupled together in any suitable fashion, as described generally herein with respect to FIG. 12 .
  • the formation of precursor component 580 by an additive manufacturing process enables precursor component 580 to be formed with a nonlinearity, structural intricacy, precision, and/or repeatability that is not achievable by other methods. Accordingly, the formation of precursor component 580 by an additive manufacturing process enables the complementary formation of core 800 (shown in FIG. 8 ), and thus of component 80, with a correspondingly increased nonlinearity, structural intricacy, precision, and/or repeatability. Additionally or alternatively, the formation of precursor component 580 using an additive manufacturing process enables the formation of internal voids 500 that could not be reliably added to component 80 in a separate process after initial formation of component 80 in a mold.
  • precursor component 580 by an additive manufacturing process using precursor material 578 that is a photopolymer or thermoplastic decreases a cost and/or a time required for manufacture of component 80, as compared to forming component 80 directly by additive manufacture using a metallic component material 78.
  • precursor component 580 is formed in any suitable fashion that enables precursor component 580 to function as described herein.
  • a suitable pattern material such as wax
  • precursor component 580 is formed from a plurality of separately formed sections that are subsequently coupled together in any suitable fashion, as described generally herein with respect to FIG. 12 .
  • FIG. 7 is a schematic perspective sectional view of a portion of an exemplary jacketed precursor component 780 that includes an exemplary jacket 700 coupled to precursor component 580.
  • jacket 700 includes at least one layer of a jacket material 778 adjacent at least a portion of a surface of precursor component 580.
  • jacket 700 includes a first jacket outer wall 792 adjacent exterior surface 592, and a second jacket outer wall 793 adjacent opposing second surface 593 of outer wall 594, such that second jacket outer wall 793 is positioned interiorly from first jacket outer wall 792.
  • Jacket outer walls 792 and 793 have shapes corresponding to exterior surface 592 and second surface 593, respectively, of precursor component outer wall 594.
  • jacket outer walls 792 and 793 are configured to separate a perimeter 806 of core 800 from an interior wall 1002 of a mold 1000 (shown in FIG. 11 ) used to form component 80 by thickness 104 of outer wall 94, as will be described herein.
  • first jacket outer wall 792 includes jacket material 778 adjacent outer wall apertures 520, such that first jacket outer wall 792 locally couples against second jacket outer wall 793 at second end 524 of outer wall apertures 520.
  • first jacket outer wall 792 locally couples against second jacket outer wall 793 at first end 522 of outer wall apertures 520.
  • Each jacketed outer wall aperture 520 defines a respective stand-off structure 720 of jacket 700 that is configured to separate perimeter 806 from interior wall 1002 by thickness 104.
  • first jacket outer wall 792 and second jacket outer wall 793 are separated at locations other than proximate stand-off structures 720 by thickness 504 of outer wall 594.
  • thickness 504 of outer wall 594 is reduced relative to thickness 104 of outer wall 94 by twice thickness 706 of jacket 700, such that a combined thickness 704 of first jacket outer wall 792, second jacket outer wall 793, and outer wall 594 corresponds to thickness 104 of outer wall 94 of component 80.
  • the at least one stand-off structure 720 has any suitable structure.
  • the at least one stand-off structure 720 is formed as a lattice between jacket outer walls 792 and 793, such as by forming outer wall apertures 520 of precursor component 580 as intersecting channels.
  • precursor component 580 does not include outer wall apertures 520.
  • jacket outer walls 792 and 793 are locally coupled together using a metal stamp (not shown) that locally collapses outer wall 594, such that first jacket outer wall 792 locally couples against second jacket outer wall 793 to form a respective stand-off structure 720.
  • jacket material 778 is adjacent opposing surfaces 597 and 599 of inner wall 596 to form opposing jacket inner walls 797 and 799 positioned interiorly from second jacket outer wall 793. Further in the exemplary embodiment, jacket material 778 is adjacent inner wall 596 adjacent inner wall apertures 502, such that inner wall apertures 502 jacketed by jacket material 778 extend through inner wall 596. Moreover, in certain embodiments, jacketed precursor component 780 continues to define the at least one internal void 500 that has a shape corresponding to the at least one void 100 of component 80. For example, in the exemplary embodiment, jacketed precursor component 780 includes at least one plenum 510, at least one chamber 512, and at least one return channel 514 (shown in FIG. 5 ).
  • jacket 700 further is adjacent opposing surfaces of partition walls 595 (shown in FIG. 5 ). Additionally or alternatively, jacket 700 is adjacent any suitable portion of the surface of precursor component 580 that enables jacketed precursor component 780 to function as described herein.
  • jacket 700 has a substantially uniform thickness 706.
  • thickness 706 varies over at least some portions of jacket 700.
  • thickness 706 is selected to be small relative to outer wall thickness 504.
  • thickness 706 also is selected such that stand-off structures 720 and/or other portions of jacket 700 provide at least a minimum selected structural stiffness such that combined thickness 704 defined by first jacket outer wall 792 and second jacket outer wall 793 is maintained when precursor material 578 is not positioned therebetween, as will be described herein.
  • jacket material 778 is selected to be at least partially absorbable by molten component material 78.
  • component material 78 is an alloy
  • jacket material 778 is at least one constituent material of the alloy.
  • jacket material 778 includes a plurality of materials disposed on precursor component 580 in successive layers, as will be described herein.
  • jacket material 778 is nickel and component material 78 is a nickel-based superalloy, and no detectable higher nickel concentration remains proximate core 800 after component material 78 is cooled, resulting in a distribution of nickel that is substantially uniform throughout the nickel-based superalloy of formed component 80.
  • thickness 706 is selected such that jacket material 778 is other than substantially absorbed by component material 78.
  • jacket material 778 is partially absorbed by component material 78, such that after component material 78 is cooled, jacket material 778 is other than substantially uniformly distributed within component material 78.
  • a concentration of jacket material 778 proximate core 800 is detectably higher than a concentration of jacket material 778 at other locations within component 80.
  • jacket material 778 is insubstantially absorbed, that is, at most only slightly absorbed, by component material 78 such that a discrete boundary delineates jacket material 778 from component material 78 after component material 78 is cooled.
  • jacket material 778 is insubstantially absorbed, that is, at most only slightly absorbed, by component material 78 such that at least a portion of jacket 700 proximate core 800 and/or at least a portion of jacket 700 proximate interior wall 1002 remains intact after component material 78 is cooled.
  • jacket 700 is formed on at least a portion of the surface of precursor component 580 by a plating process, such that jacket material 778 is deposited on precursor component 580 until the selected thickness 706 of jacket 700 is achieved.
  • jacket material 778 is a metal, and is deposited on precursor component 580 in a suitable metal plating process.
  • jacket material 778 is deposited on precursor component 580 in an electroless plating process.
  • jacket material 778 is deposited on precursor component 580 in an electroplating process.
  • jacket material 778 is any suitable material, and jacket 700 is formed on precursor component 580 by any suitable plating process that enables jacket 700 to function as described herein.
  • jacket material 778 includes a plurality of materials disposed on precursor component 580 in successive layers.
  • precursor material 578 is a thermoplastic
  • an initial layer of jacket material 778 is a first metal alloy selected to facilitate electroless plating deposition onto precursor material 578
  • a subsequent layer of jacket material 778 is a second metal alloy selected to facilitate electroplating to the prior layer of jacket material 778.
  • each of the first and second metal alloys are alloys of nickel.
  • precursor material 578 is any suitable material
  • jacket material 778 is any suitable plurality of materials
  • jacket 700 is formed on precursor component 580 by any suitable process that enables jacket 700 to function as described herein.
  • jacketed precursor component 780 is formed from a unitary precursor component 580. In alternative embodiments, jacketed precursor component 780 is formed from a precursor component 580 that is other than unitarily formed.
  • FIG. 12 is a schematic perspective exploded view of a portion of another exemplary jacketed precursor component 780 that may be used to form component 80 shown in FIG. 2 .
  • jacketed precursor component 780 includes precursor component 580 formed from a plurality of separately formed sections 1280 coupled together.
  • one of internal voids 500 defines an internal pipe bounded by specified portions of precursor component inner wall 596 and/or partition walls 595.
  • the internal pipe extends to a depth within precursor component 580 for which a selected plating process would not be effective to reliably deposit jacket 700 on the specified portions of precursor component inner wall 596 and/or partition walls 595 of a unitary precursor component 580.
  • precursor component 580 includes a pair of separately formed "half-pipe" sections such that the specified portions of precursor component inner wall 596 and/or partition walls 595 are exposed along their full depth, and each half-pipe section is separately plated with jacket 700 prior to coupling the sections together to form jacketed precursor component 780.
  • jacket 700 is formed on the assembled precursor component 580 subsequent to coupling together of the sections of precursor component 580.
  • jacket 700 is formed in any suitable fashion.
  • jacket 700 is formed using a process that does not involve precursor component 580.
  • jacket 700 is formed at least partially using a suitable additive manufacturing process, and jacket material 778 is selected to facilitate additive manufacture of jacket 700.
  • a computer design model of jacket 700 is developed from a computer design model of component 80, with preselected thickness 706 of jacket 700 added in the computer design model adjacent selected surfaces of component 80 and stand-off structures 720 added at selected locations within outer wall 94, as described above, and then component 80 itself is removed from the computer design model.
  • the computer design model for jacket 700 is sliced into a series of thin, parallel planes, and a computer numerically controlled (CNC) machine deposits successive layers of jacket material 778 from a first end to a second end of jacket 700 in accordance with the model slices to form jacket 700.
  • the successive layers of jacket material 778 are deposited using at least one of a direct metal laser melting (DMLM) process, a direct metal laser sintering (DMLS) process, and a selective laser sintering (SLS) process.
  • DMLM direct metal laser melting
  • DMLS direct metal laser sintering
  • SLS selective laser sintering
  • jacket 700 is formed using another suitable additive manufacturing process. It should be understood that in certain embodiments, jacket 700 is formed from a plurality of separately additively manufactured sections that are subsequently coupled together, such as around a separately formed core 800, in any suitable fashion.
  • the formation of jacket 700 by an additive manufacturing process enables jacket 700 to be formed with a nonlinearity, structural intricacy, precision, and/or repeatability that is not achievable by other methods. Accordingly, the formation of jacket 700 by an additive manufacturing process enables the complementary formation of core 800 (shown in FIG. 8 ), and thus of component 80, with a correspondingly increased nonlinearity, structural intricacy, precision, and/or repeatability. Additionally or alternatively, the formation of jacket 700 using an additive manufacturing process enables the formation of internal voids 500 that could not be reliably added to component 80 in a separate process after initial formation of component 80 in a mold. Moreover, in some embodiments, the formation of jacket 700 by an additive manufacturing process decreases a cost and/or a time required for manufacture of component 80, as compared to forming component 80 directly by additive manufacture using component material 78.
  • FIG. 8 is a schematic perspective sectional view of a portion of an exemplary jacketed cored precursor component 880 that includes exemplary core 800 within jacketed precursor component 780. More specifically, core 800 is positioned interiorly from second jacket outer wall 793, such that perimeter 806 of core 800 is coupled against second jacket outer wall 793. Thus, core 800 is located within the at least one internal void 500 of jacketed precursor component 780.
  • core 800 includes at least one plenum core portion 810, at least one chamber core portion 812, and at least one return channel core portion 814 (shown in FIG.
  • core 800 includes inner wall aperture core portions 802 positioned in inner wall apertures 502 of jacketed precursor component 780, and inner wall aperture core portions 802 are configured to define inner wall apertures 102 when component 80 is formed.
  • inner wall 596 does not include inner wall apertures 502, and core 800 correspondingly does not include core portions 802.
  • component 80 is initially formed without inner wall apertures 102, and inner wall apertures 102 are added to component 80 in a subsequent process.
  • core material 878 is selected based on a compatibility with, and/or a removability from, component material 78. Additionally or alternatively, core material 878 is selected based on a compatibility with jacket material 778. For example, in some such embodiments, core material 878 is selected to have a matched thermal expansion coefficient to that of jacket material 778, such that during core firing, core 800 and jacket 700 expand at the same rate, thereby reducing or eliminating stresses, cracking, and/or other damaging of the core due to mismatched thermal expansion. In alternative embodiments, core material 878 is any suitable material that enables component 80 to be formed as described herein.
  • the filler material is inserted into each stand-off structure 720 such that a shape of second jacket outer wall 793 corresponds to the interior shape of component outer wall 94 proximate stand-off structures 720.
  • the filler material is a wax material.
  • the filler material is removed from mold 1000 as slag after molten component material 78 is introduced into the at least one jacketed cavity 900.
  • the filler material facilitates preventing core material 878 from entering into stand-off structures 720 when core 800 is formed.
  • the filler material is not used and core material 878 is allowed to penetrate to some extent into stand-off structures 720.
  • closures 722 are not present, enabling core material 878 to flow into outer wall apertures 520 to define the openings through outer wall 594.
  • core 800 is formed and positioned in any suitable fashion that enables core 800 to function as described herein.
  • core material 878 is injected as a slurry into a suitable core die (not shown), dried, and fired in a separate core-forming process to form core 800.
  • sections of jacketed precursor component 580 are coupled around the separately formed core 800 to form jacketed cored precursor component 880.
  • sections of jacket 700 are decoupled from, or formed without using, precursor component 580, and the sections of jacket 700 are coupled around the separately formed core 800 to form jacketed core 980.
  • jacket 700 is decoupled from, or formed without using, precursor component 580, and core material 878 is added as a slurry to jacket 700 and fired within jacket 700 to form core 800 within jacketed core 980.
  • Jacketed core 980 defines at least one jacketed cavity 900 therewithin.
  • Each at least one jacketed cavity 900 is configured to receive molten component material 78 therein to form a corresponding portion of component 80. More specifically, molten component material 78 is added to the at least one jacketed cavity 900 and cooled, such that component material 78 and jacket material 778 bounded by core 800 and/or interior wall 1002 at least partially define the corresponding portion of component 80, as will be described herein.
  • first jacket outer wall 792 and second jacket outer wall 793 define at least one jacketed cavity 900, designated as at least one outer wall jacketed cavity 994, therebetween.
  • jacket 700 separates perimeter 806 from interior wall 1002 of mold 1000 (shown in FIG. 11 ) by thickness 104 of component outer wall 94 (shown in FIG. 4 ).
  • stand-off structures 720 have sufficient stiffness such that a combined thickness 904 of first jacket outer wall 792, second jacket outer wall 793, and outer wall jacketed cavity 994 corresponds to combined thickness 704 of first jacket outer wall 792, second jacket outer wall 793, and precursor component outer wall 594, and thus corresponds to thickness 104 of component outer wall 94.
  • a shape of the at least one outer wall jacketed cavity 994 corresponds to a shape of outer wall 94 of component 80 at locations other than proximate stand-off structures 720.
  • jacketed core 980 defines the at least one jacketed cavity 900 having a shape corresponding to any suitable portion of component 80 for use in any suitable application.
  • precursor material 578 is selected to facilitate removal of precursor component 580 from within jacketed cored precursor component 880 to form jacketed core 980.
  • precursor material 578 is selected to have an oxidation or auto-ignition temperature that is less than a melting point of jacket material 778.
  • a temperature of jacketed precursor component 780 is raised to or above the oxidation temperature of precursor material 578, such that precursor component 580 is oxidized or burned out of jacket 700.
  • precursor component 580 is oxidized at least partially simultaneously with a firing of core 800 within jacketed cored precursor component 880.
  • precursor material 578 is oxidized and/or otherwise removed prior to firing core 800 within jacketed cored precursor component 880. Additionally or alternatively, precursor material 578 is melted and drained from within jacketed cored precursor component 880.
  • precursor material 578 is selected to be a softer material than jacket material 778, and precursor component 580 is machined out of jacketed precursor component 780.
  • a mechanical rooter device is snaked into jacket 700 to break up and/or dislodge precursor material 578 to facilitate removal of precursor component 580.
  • precursor material 578 is selected to be compatible with a chemical removal process, and precursor component 580 is removed from jacket 700 using a suitable solvent.
  • precursor material 578 is any suitable material that enables precursor component 580 to be removed from within jacketed precursor component 780 in any suitable fashion.
  • jacket 700 is formed by a process that does not include any use of precursor component 580, as described above, such that no precursor material 578 needs to be removed to form jacketed core 980.
  • core 800 includes, as described above, the at least one plenum core portion 810 positioned interiorly from second jacket inner wall 799, the at least one chamber core portion 812 positioned between first jacket inner wall 797 and second jacket outer wall 793, and inner wall aperture core portions 802 extending through the at least one inner wall jacketed cavity 996.
  • core 800 also includes the at least one return channel core portion 814 (shown in FIG. 10 ).
  • jacket 700 provides a skeleton structure within jacketed core 980 that facilitates positioning the plurality of portions of core 800 with respect to each other and, subsequently, with respect to mold 1000 (shown in FIG. 10 ).
  • core 800 is configured to correspond to any other suitable configuration of the at least one internal void 100 that enables component 80 to function for its intended purpose.
  • FIG. 10 is a schematic perspective view of an exemplary mold assembly 1001 that includes jacketed core 980 and may be used to form component 80 shown in FIGs. 2-4 .
  • FIG. 11 is a schematic perspective sectional view of a portion of mold assembly 1001, taken along lines 11-11 in FIG. 10 , and including the portion of jacketed core 980 shown in FIG. 9 .
  • mold assembly 1001 includes jacketed core 980 positioned with respect to mold 1000.
  • An interior wall 1002 of mold 1000 defines a mold cavity 1003 within mold 1000, and jacketed core 980 is at least partially received in mold cavity 1003.
  • interior wall 1002 defines a shape corresponding to an exterior shape of component 80, such that first jacket outer wall 792, which also has a shape corresponding to the exterior shape of component 80 at locations other than proximate stand-off structures 720, is coupled against interior wall 1002.
  • jacket 700 separates core perimeter 806 from interior wall 1002 by thickness 104 of component outer wall 94, as discussed above, such that molten component material 78 is receivable within at least one jacketed cavity 900 defined between jacket outer walls 792 and 793 to form outer wall 94 having preselected thickness 104. More specifically, in the exemplary embodiment, the at least one stand-off structure 720 maintains combined thickness 904 of first jacket outer wall 792, second jacket outer wall 793, and outer wall jacketed cavity 994 at locations other than proximate stand-off structures 720.
  • jacket material 778 of jacket outer walls 792 and 793 is substantially absorbed by molten component material 78 to form outer wall 94, while in other embodiments, for example, jacket outer walls 792 and 793 remain at least partially intact adjacent component material 78 within outer wall 94, as described above.
  • core 800 is shaped to correspond to a shape of at least one internal void 100 of component 80, such that core 800 of jacketed core 980 positioned within mold cavity 1003 defines the at least one internal void 100 within component 80 when component 80 is formed.
  • the at least one inner wall jacketed cavity 996 is configured to receive molten component material 78, such that the at least one plenum core portion 810, the at least one chamber core portion 812, and/or the inner wall aperture core portions 802 adjacent the at least one inner wall jacketed cavity 996 cooperate to define inner wall 96 of component 80.
  • the at least one plenum core portion 810 defines the at least one plenum 110 interiorly of inner wall 96
  • the at least one chamber core portion 812 defines the at least one chamber 112 between inner wall 96 and outer wall 94
  • the inner wall aperture core portions 802 define inner wall apertures 102 extending through inner wall 96.
  • the at least one return channel core portion 814 defines the at least one return channel 114 at least partially defined by inner wall 96.
  • core 800 is removed from component 80 to form the at least one internal void 100.
  • core material 878 is removed from component 80 using a chemical leaching process.
  • Mold 1000 is formed from a mold material 1006.
  • mold material 1006 is a refractory ceramic material selected to withstand a high temperature environment associated with the molten state of component material 78 used to form component 80.
  • mold material 1006 is any suitable material that enables component 80 to be formed as described herein.
  • mold 1000 is formed by a suitable investment process. For example, but not by way of limitation, jacketed core 980 is repeatedly dipped into a slurry of mold material 1006 which is allowed to harden to create a shell of mold material 1006, and the shell is fired to form mold 1000.
  • mold 1000 is formed by any suitable method that enables mold 1000 to function as described herein.
  • exemplary method 1300 of forming a component, such as component 80, having an outer wall of a predetermined thickness, such as outer wall 94 having predetermined thickness 104, is illustrated in a flow diagram in FIGs. 13-14 .
  • exemplary method 1300 includes introducing 1326 a component material, such as component material 78, in a molten state into at least one jacketed cavity, such as at least one jacketed cavity 900, defined in a mold assembly, such as mold assembly 1001.
  • the mold assembly includes a jacketed core, such as jacketed core 980, positioned with respect to a mold, such as mold 1000.
  • method 1300 also includes locally coupling 1318 the first jacket outer wall to the second jacket outer wall to define at least one stand-off structure, such as stand-off structure 720, that separates the perimeter from the interior wall by the predetermined thickness.
  • stand-off structure 720 that separates the perimeter from the interior wall by the predetermined thickness.
  • method 1300 further includes separately forming 1304 a plurality of precursor component sections, such as precursor component sections 1280, and coupling 1310 the plurality of sections together to form the precursor component.
  • the step of forming 1312 the jacket includes forming 1306 the jacket on each of the sections prior to the step of coupling 1310 the sections together, and method 1300 also includes masking 1308 at least one mating surface, such as mating surface 1202, of the plurality of sections prior to the step of forming 1306 the jacket, such that deposition of the jacket material on the at least one mating surface is inhibited.
  • method 1300 also includes forming 1324 the mold around the jacketed core by an investment process, as described above.
  • the jacketed core automatically provides the preselected outer wall thickness without use of locating pins, thus reducing a time and cost of preparing the mold assembly for prototyping or production operations.
  • the above-described embodiments enable formation of components having relatively thin outer walls that cannot be precisely and/or repeatably formed using other known mold assemblies and methods.
  • An exemplary technical effect of the methods, systems, and apparatus described herein includes at least one of: (a) reducing or eliminating fragility problems associated with forming, handling, transport, and/or storage of a core used in forming a component having a preselected outer wall thickness; (b) improving precision and repeatability of formation of components having an outer wall of a predetermined thickness, particularly, but not limited to, components having relatively thin outer walls; and (c) enabling casting of components having an outer wall of a predetermined thickness without use of locating pins.
  • Exemplary embodiments of mold assemblies and methods including jacketed cores are described above in detail.
  • the jacketed cores, and methods and systems using such jacketed cores are not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein.
  • the exemplary embodiments can be implemented and utilized in connection with many other applications that are currently configured to use cores within mold assemblies.

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US10286450B2 (en) 2019-05-14
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EP3238859A1 (en) 2017-11-01
KR102261351B1 (ko) 2021-06-09
JP6924063B2 (ja) 2021-08-25
US20190217381A1 (en) 2019-07-18
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US20170312815A1 (en) 2017-11-02
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